AD/GAZELLE/24 - Main Rotor Head - Free-Wheel and Clutch

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B10243 In force Legislative Instrument

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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 


AIRWORTHINESS DIRECTIVE


For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

 

Eurocopter SA341 and SA342 (Gazelle) Series Helicopters

 

AD/GAZELLE/24 Main Rotor Head - Free-Wheel and Clutch 10/2002

 

Applicability: SA 341G and SA 342J helicopters fitted with clutch assemblies part number (P/N) 341A35-0010 all dash numbers, 341A35-0011 all dash numbers, and 341A35-0050 all dash numbers.

Requirement: Replace clutch/free-wheel and clutch/torquemeter shaft attachment bolts in accordance with Eurocopter SA 341/ 342 Service Bulletin 65.58 Revision 1.

Note: DGAC 2002-363-042A refers.

 

Compliance: Unless previously accomplished; within 50 hours time in service from the effective date of this Directive.

This Airworthiness Directive becomes effective on 3 October 2002.

 

Background: This Directive requires the replacement of the clutch assembly clutch/free-wheel and clutch/torquemeter shaft assembly bolts. This requirement reflects an error in bolt part numbers previously listed in the IPC. The bolt listed was not compliant. The plain section of the bolt is 1 mm longer than required. The bolt may become thread bound on the shank of the bolt before achieving the preload on the assembly dur ing installation. Subsequent failure of the bolt head may occur involving separation of the bolt head.


 

James Coyne

Delegate of the Civil Aviation Safety Authority 23 August 2002

 


The above AD is notified in the Commonwealth of Australia Gazette on 11 September 2002.

 

 


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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.